Federal Register / Vol. 76, No. 84 / Monday, May 2, 2011 / Rules and Regulations 24351 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle ACO 

to make those findings. For a repair method 

to be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

Related Information 

(k) For more information about this AD, 

contact Kenneth Paoletti, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

917–6434; fax (425) 917–6590; 

kenneth.paoletti@faa.gov. 

Material Incorporated by Reference 

(l) You must use Boeing Alert Service 

Bulletin 747–54A2232, dated April 15, 2010, 

to do the actions required by this AD, unless 

the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Boeing Alert Service Bulletin 747–54A2232, 

dated April 15, 2010, under 5 U.S.C. 552(a) 

and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; e-mail me.boecom@boeing.com; 

Internet https:// 

www.myboeingfleet.com. 

(3) You may review copies of the service 

information at the FAA, FAA, Transport 

Airplane Directorate, 1601 Lind Avenue, 

SW., Renton, Washington. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call 202–741– 

6030, or go to http://www.archives.gov/

federal_register/code_of_federal_regulations/

ibr_locations.html. 

Issued in Renton, Washington, on April 15, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–9919 Filed 4–29–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0383; Directorate 

Identifier 2010–NM–093–AD; Amendment 

39–16675; AD 2011–09–13] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A340–200 and –300 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

Further to accomplishment of A340 ALI 

tasks 545104, which require a rototest 

inspection as per Non Destructive Testing 

Manual (NTM) 54–51–04 of engine pylon 

pyramid attachment areas at aft end of lower 

arms between Rib 1 and Rib 2 (2 fastener 

locations/pylon), four findings have been 

reported and repaired. 

* * * * * 

The unsafe condition is cracking, which 

might impact the structural integrity of 

the airplane. This AD requires actions 

that are intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective May 

17, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of May 17, 2011. 

We must receive comments on this 

AD by June 16, 2011. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–40, 1200 New Jersey 

Avenue, SE., Washington, DC, between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone: 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone: 

425–227–1138; fax: 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2008–0140, 

dated July 28, 2008 (referred to after this 

as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

Further to accomplishment of A340 ALI 

tasks 545104, which require a rototest 

inspection as per Non Destructive Testing 

Manual (NTM) 54–51–04 of engine pylon 

pyramid attachment areas at aft end of lower 

arms between Rib 1 and Rib 2 (2 fastener 

locations/pylon), four findings have been 

reported and repaired. 

Further investigations made on 

performances of High Frequency Eddy 

Current (HFEC) inspection techniques in 

steel led to the conclusion that existing NTM 

procedure 54–51–04 by rototest is not 

reliable because this method is not adapted 

to the ferromagnetic materials and therefore 

findings reported up to now using this 

procedure can be considered as uncertain. 

Therefore, a new inspection procedure 

using Ultra Sonic (US) testing without 

fastener removal has been developed. 

In order to comply with certification 

requirements, this Airworthiness Directive 

(AD) requires performing the new [repetitive] 

US inspection [for cracking] on all A340– 

200/–300 pre-modification 49203 

(reinforcements of pylon primary structure 

for enhanced A340). 


jlentini on DSKJ8SOYB1PROD with RULES
24352 Federal Register / Vol. 76, No. 84 / Monday, May 2, 2011 / Rules and Regulations 

The unsafe condition is cracking, which 

might impact the structural integrity of 

the airplane. The required actions 

include repairing any cracks found. You 

may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A340–54–4010, including 

Appendices 1, 2, and 3, dated July 21, 

2008. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

There are no products of this type 

currently registered in the United States. 

However, this rule is necessary to 

ensure that the described unsafe 

condition is addressed if any of these 

products are placed on the U.S. Register 

in the future. 

Differences Between the AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 

Any such differences are highlighted in 

a note within the AD. 

FAA’s Determination of the Effective 

Date 

Since there are currently no domestic 

operators of this product, notice and 

opportunity for public comment before 

issuing this AD are unnecessary. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2011–0383; 

Directorate Identifier 2010–NM–093– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2011–09–13 Airbus: Amendment 39–16675. 

Docket No. FAA–2011–0383; Directorate 

Identifier 2010–NM–093–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective May 17, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A340– 

211, –212, –213, –311, –312, and –313 

airplanes; certificated in any category; all 

serial numbers except those on which Airbus 

Modification 49203 has been incorporated in 

production. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 54: Nacelles/Pylons. 

Reason 

(e) The mandatory continued airworthiness 

information (MCAI) states: 

Further to accomplishment of A340 ALI 

tasks 545104, which require a rototest 

inspection as per Non Destructive Testing 

Manual (NTM) 54–51–04 of engine pylon 

pyramid attachment areas at aft end of lower 

arms between Rib 1 and Rib 2 (2 fastener 

locations/pylon), four findings have been 

reported and repaired. 

* * * * * 

The unsafe condition is cracking, which 

might impact the structural integrity of the 

airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 


jlentini on DSKJ8SOYB1PROD with RULES
Federal Register / Vol. 76, No. 84 / Monday, May 2, 2011 / Rules and Regulations 24353 

Ultrasonic Inspection 

(g) At the later of the compliance times 

specified in paragraphs (g)(1) and (g)(2) of 

this AD, except as provided by paragraph (h) 

of this AD: Perform an ultrasonic inspection 

of pylon pyramid attachment areas at the aft 

end of the lower arms between Rib 1 and Rib 

2 without fastener removal (2 fastener 

locations per pylon), in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A340–54–4010, 

dated July 21, 2008. 

(1) Before the accumulation of the 

applicable total flight cycles or total flight 

hours, whichever occurs first, specified in 

table 1 of this AD. 

(2) Within 90 days after the effective date 

of this AD. 

TABLE 1—INITIAL INSPECTION COMPLIANCE TIMES

Weight variant Total flight 

cycles 

Total flight 

hours 

000 through 004 .............................................................................................................................................................. 13,000 60,000 

020, 021, 023 through 026, 028 through 030, Pre 49203 .............................................................................................. 11,470 77,400 

027 ................................................................................................................................................................................... 11,000 30,000 

(h) For airplanes belonging to weight 

variant 000 through 004 inspected before the 

effective date of this AD in accordance with 

Airworthiness Limitations Items (ALI) Task 

545104–01–01, as described in Airbus A340 

Airworthiness Limitations Items Document 

Ref: AI/SE–M4/95A.0051/97, Issue 10, dated 

February 1, 2007: Perform the inspection 

required in paragraph (g) of this AD at the 

compliance times specified in paragraphs 

(h)(1) and (h)(2) of this AD, whichever occurs 

later. 

(1) Within 90 days after the effective date 

of this AD. 

(2) Within 2,680 flight cycles or 19,200 

flight hours, whichever occurs first, after the 

most recent rototest inspection done in 

accordance with ALI task 545104–01–01, but 

not to exceed the accumulation of 15,280 

total flight cycles or 76,400 total flight hours, 

whichever occurs first. 

(i) If no cracking is detected during any 

inspection required by paragraph (g) of this 

AD: Repeat the inspection required in 

paragraph (g) of this AD thereafter at 

intervals not to exceed the earlier of the 

applicable flight cycles or flight hours 

interval specified in table 2 of this AD. 

TABLE 2—REPETITIVE INSPECTION INTERVAL

Weight variant Flight cycles Flight hours 

000 through 004 .............................................................................................................................................................. 1,900 9,500 

020, 021, 023 through 026, 028 through 030, Pre 49203 .............................................................................................. 1,700 8,500 

027 ................................................................................................................................................................................... 1,700 8,500 

(j) If any crack is detected during any 

inspection required by this AD: Before 

further flight, repair the cracking using a 

method approved by either the Manager, 

International Branch, ANM 116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA) (or its 

delegated agent). 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(k) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone: 425–227–1138; fax: 425– 

227–1149. Information may be e-mailed to: 

9-ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Special Flight Permits: Special flight 

permits, as described in Section 21.197 and 

Section 21.199 of the Federal Aviation 

Regulations (14 CFR 21.197 and 21.199), are 

not allowed if any crack is detected during 

any inspection required by this AD. 

Related Information 

(l) Refer to MCAI EASA Airworthiness 

Directive 2008–0140, dated July 28, 2008; 

and Airbus Mandatory Service Bulletin 

A340–54–4010, dated July 21, 2008; for 

related information. 

Material Incorporated by Reference 

(m) You must use Airbus Mandatory 

Service Bulletin A340–54–4010, including 

Appendices 1, 2, and 3, dated July 21, 2008, 

to do the actions required by this AD, unless 

the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone: +33 

5 61 93 36 96; fax: +33 5 61 93 45 80; e-mail: 

airworthiness.A330-A340@airbus.com; 

Internet: http://www.airbus.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on April 15, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–9921 Filed 4–29–11; 8:45 am] 

BILLING CODE 4910–13–P 


jlentini on DSKJ8SOYB1PROD with RULES